A thermostat is a type of contact inductive device. It has the features of being compact, lightweight, and high temperature control precision. A scheme for using a thermostat as a control device in the active electrical heating and temperature control circuit of the spacecraft is proposed. It is in line with the design requirement of the spacecraft thermal control system when the computer controlled heater-system is limited. Compared with the computer-controlled heater system, the thermostat-controlled heater system has the advantages of simple configuration, easy implementation, and high reliability under certain conditions. The thermal design of the shunt regulator, manipulator, portable light, and emergency brake device is analysed given the characteristics of the demands on manned spacecraft. The use of a thermostat to solve the temperature control problem when a computer is not available is a common feature of these thermal designs. The temperature results of the on-orbit test and ground test prove that using a thermostat in the heater system of spacecraft can ensure equipment is within the range of index requirement reliably.
As one kind of large-scale on-orbit deployable motion mechanism, the launch state of the manipulator on the Chinese Space Station is fixed on the external surface of the Tian-He module by 41 locking-releasing devices. It covers an area of 3.5 meters in arc length and 4.6 meters in length. The locking-releasing device should not only be able to withstand the environmental load conditions of the launch stage and in-orbit stage but also can release the manipulator reliably after going through the thermal and dynamic changes. Three factors cause the deformation of the locking-releasing device before unlocking the manipulator. The first deformation is caused by the module from the atmospheric conditions to the vacuum conditions. The second deformation is thermal deformation which is caused by the temperature changes in the module and manipulator. The locking-releasing devices bear the overload force during the launch stage will cause the third deformation. The numerical simulating analysis shows that the deformation is not beyond the allowable range. The manipulator was unlocked successfully after it was launched together with the Tian-He module. It is verified that the deformation caused by the change of thermo-mechanical conditions from the launch stage to the orbit stage does not affect the unlocking performance of the locking-releasing device.
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